Guide blade fixture in a flow channel of an aircraft gas turbine

Abstract

An arrangement for detachably fixing a guide blade segment that forms part of a transition channel of an aircraft gas turbine comprises high-pressure and low-pressure turbines. The arrangement has a groove-hook-type connection in the front area of the outer platform of the guide blade segment for its radial fixation and at least one pin that penetrates the hook-groove-type connection for securing it against rotation of the guide blade segment.

Description

BACKGROUND AND SUMMARY OF THE INVENTION[0001]This invention relates to an arrangement for fixing a guide blade segment that forms part of a transition channel.[0002]Modern aircraft gas turbines frequently comprise a so-called core engine with a high-pressure turbine having a relatively small diameter, which is arranged downstream from a low-pressure turbine having a relatively large diameter. This creates the necessity of transitioning the ring channel, which extends through the gas turbine and is equipped with guide blades, behind the high-pressure turbine from its small diameter to the large diameter of the low-pressure turbine, which occurs with the aid of a so-called transition channel.[0003]Such engines furthermore have high bypass ratios and low speeds of the low-pressure turbine shaft, which is generally separated in relation to the high-pressure turbine shaft; moreover the urgency exists to design the core engines in an increasingly compact and powerful manner, which leads t...

AI Technical Summary

Benefits of technology

"The invention is a new arrangement for fixing a guide blade segment in a gas turbine engine. The arrangement is simple and easy to install, while also being effective in sealing the transition channel. The design uses a groove-hook-type connection and hooks on the outer platform of the guide blade segment for secure attachment to the turbine housing. This arrangement also allows for a locking element for the transition channel, which further simplifies the design. The invention is lightweight and cost-effective, and can be easily produced."

Problems solved by technology

Such engines furthermore have high bypass ratios and low speeds of the low-pressure turbine shaft, which is generally separated in relation to the high-pressure turbine shaft; moreover the urgency exists to design the core engines in an increasingly compact and powerful manner, which leads to increasingly longer axially extending transition channels with greater differences between the radii of the channel cross-sections that need to be taken into consideration.

Hence, no integral, inherently stable guide blade segments exist.

In the area of the guide elements (22, 24, 26, 28), the design is relatively complex as well problematic from a stability point of view.

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